【摘要】：隨著世界各國航空航天事業(yè)的發(fā)展,各種高速飛行器逐漸涌現(xiàn),飛行器的姿態(tài)測量成為控制系統(tǒng)的重要技術(shù)問題之一。傳統(tǒng)的慣性導(dǎo)航系統(tǒng)將不能完全適應(yīng)當(dāng)今的飛行器控制的需求,衛(wèi)星導(dǎo)航系統(tǒng)日益完善,具有全天候、無誤差積累等優(yōu)點,其應(yīng)用領(lǐng)域不再局限于傳統(tǒng)單點定位、授時等。差分技術(shù)應(yīng)用作為新興的領(lǐng)域,使得衛(wèi)星導(dǎo)航接收機應(yīng)用于飛行器姿態(tài)測量成為可能,是未來發(fā)展的趨勢。本課題研究一種利用衛(wèi)星導(dǎo)航接收機測量飛行器姿態(tài)的技術(shù)。通過接收衛(wèi)星信號,載波相位做差分的方法,解算出高精度的基線向量,從而確定姿態(tài)角來實現(xiàn)姿態(tài)的測量。本文從理論出發(fā),首先介紹了飛行器姿態(tài)測量的原理,確定利用衛(wèi)星導(dǎo)航接收機測量飛行器姿態(tài)的方法。其次研究了飛行器姿態(tài)測量的關(guān)鍵技術(shù),以導(dǎo)彈為例,分析飛行器姿態(tài)測量中對天線的布局、方向圖、增益的要求。探討姿態(tài)測量觀測方程及載波相位差分技術(shù),建立了飛行器姿態(tài)解算的數(shù)學(xué)模型。討論姿態(tài)解算中載波相位整周模糊度的求解算法,詳細分析LAMBDA算法求解載波相位整周模糊度的流程。并且應(yīng)用MATLAB仿真,對姿態(tài)角求解算法進行驗證和精度分析。闡述周跳產(chǎn)生的原因,研究周跳的檢測和修復(fù)方法。最后根據(jù)前述理論研究,設(shè)計單基線飛行器姿態(tài)測量接收機硬件平臺。射頻前端采用MAX2769作為主芯片,對天線接收的射頻模擬信號進行放大、濾波、下變頻、AD轉(zhuǎn)換等處理。數(shù)字部分采用SOC作為核心處理器,單芯片內(nèi)實現(xiàn)基帶數(shù)字信號的處理和姿態(tài)測量算法的解算,提高了系統(tǒng)的集成度。經(jīng)過實際的對天測試,分別以基線長度為5米和5.9米測量多組數(shù)據(jù)。俯仰角和偏航角的測量誤差基本在0.5度以內(nèi)。
[Abstract]:With the development of aerospace industry all over the world, a variety of high-speed aircraft have emerged gradually. Attitude measurement of aircraft has become one of the important technical problems of control system. The traditional inertial navigation system will not be able to fully meet the needs of today's aircraft control. The satellite navigation system is becoming more and more perfect, with the advantages of all-weather, no error accumulation, etc. Its application fields are no longer limited to the traditional single-point positioning, timing and so on. The application of differential technology as a new field makes it possible for satellite navigation receivers to be used in attitude measurement of aircraft, which is the trend of future development. In this paper, a technique of attitude measurement using satellite navigation receiver is studied. By receiving the satellite signal and making the carrier phase difference, the high precision baseline vector is solved and the attitude angle is determined to realize the attitude measurement. In this paper, the theory of attitude measurement is introduced firstly, and the method of attitude measurement using satellite navigation receiver is determined. Secondly, the key technology of aircraft attitude measurement is studied. Taking missile as an example, the requirements of antenna layout, pattern and gain are analyzed. The attitude observation equation and carrier phase difference technique are discussed, and the mathematical model of attitude calculation for aircraft is established. The algorithm for solving carrier phase integer ambiguity in attitude resolution is discussed, and the flow of LAMBDA algorithm to solve carrier phase integer ambiguity is analyzed in detail. MATLAB simulation is used to verify and analyze the accuracy of attitude angle algorithm. The causes of cycle jump are expounded, and the detection and repair methods of cycle jump are studied. Finally, the hardware platform of attitude measurement receiver for single baseline vehicle is designed according to the above theoretical research. The RF front-end uses MAX2769 as the main chip to amplify, filter, downconversion and AD transform the RF analog signals received by the antenna. In the digital part, SOC is used as the core processor, and the baseband digital signal processing and attitude measurement algorithm are realized in a single chip, which improves the integration of the system. After the actual test, the baseline length of 5 meters and 5.9 meters were used to measure the data. The measurement error of pitch angle and yaw angle is within 0.5 degree.
【學(xué)位授予單位】：北方工業(yè)大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2017
【分類號】：V249;TN967.1

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